CN2934073Y - Airplane test wheel fender - Google Patents
Airplane test wheel fender Download PDFInfo
- Publication number
- CN2934073Y CN2934073Y CNU200520036382XU CN200520036382U CN2934073Y CN 2934073 Y CN2934073 Y CN 2934073Y CN U200520036382X U CNU200520036382X U CN U200520036382XU CN 200520036382 U CN200520036382 U CN 200520036382U CN 2934073 Y CN2934073 Y CN 2934073Y
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- CN
- China
- Prior art keywords
- primary structure
- ground
- structure member
- crank
- test run
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- Expired - Lifetime
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- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The utility model disclose a ground check wheel block for aircraft, which comprises an arc-shaped bracing plate and a diagonal bracing stressed member for supporting aircraft wheels, wherein the diagonal stressed member consists of a standing plate connected fixedly to rear part of the arc-shaped bracing plate, a diagonal bracing stressed member connected fixedly to back of the standing plate and a horizontal bracing stressed member connected fixedly between the standing plate and the diagonal bracing stressed member; two sides of the formed triangle supporting framework are provided with hand push rods which are rotatably connected and have active rocking arms, to the rotary kinematic pair of the active rocking arms being connected a crank slider connecting rod mechanism which consists of crank forks and also being connected ground wheels which are mounted on the crank forks. With the movement of the crank slider connecting rod mechanism, the utility model conforms the motion trajectories of the hand push rods and the ground wheels to the requirements before and after the plane is used; and also facilitates the ground check wheel block to transmit the thrusting force of the motor directly to the grooves of the ground check flat and the wheel to contact with the ground in transportation. The utility model provides a convenient and rapid carrying method for ground personnel and avoids the defect of high carrying intensity due to large volume and heavy weight.
Description
Technical field:
The utility model relates to a kind of aircraft test run catch, specifically, when the utility model relates to the airplane engines ground test run, bears the huge thrust of driving engine, keeps out the test run catch of undercarriage creeping of tyre.
Background technology
For ensureing the safety of airplane engines ground test run, often to can bear the huge thrust of engine test to the setting of undercarriage wheel, prevent the test run catch of aircraft displacement.Aircraft test run catch mainly is welded to form by the catch of steel structure at present, and its basic structure is steel plate or steel pipe (pipe or rectangular tube) welding or adopts aluminium alloy casting.The body body is big stupid thick, and weight is very heavy, and in the use, the ground maintenance personnel want armrest to propose carrying, and labour intensity is big, uses very inconvenient.Change the problems referred to above of aero-engine test run catch, must solve from two aspects.The one, reduce structural weight, the 2nd, manage to change laborer's force mechanism, to reduce ground maintenance personnel's labour intensity.Reducing on the structural weight, can aspect two, carry out, the one, change power transmission, the 2nd, select light material.Because the power transmission of the test run catch of aero-engine is more direct, and will bear the huge thrust of aero-engine, therefore, it is infeasible to reach the change structural weight by the change power transmission.Aspect the selection material, the use of steel or aluminum alloy can not solve weight issue at all.If adopt other light material, the rising significantly that then can bring cost.Chinese patent CN97212904.9 disclosed " a kind of catch that is used for the aircraft test run ", adopt iron-clad horses palm shape steel plate as the catch main body, the bottom surface of main body is fixed with the anti-slip rubber pad, four wheels are housed on the main body, by rising and falling of handle, gear and drive link control wheel, main body afterbody opening part is equiped with locking bar, leads the catch gear that knee and lock pin are formed, main body and catch gear can pin aircraft wheel, move forward in order to prevent that wheel breaks away from catch or drags catch when brake was lost efficacy.The weak point of this patent is a complex structure, the manufacturing cost height, and catch gear will pin aircraft wheel.
Summary of the invention:
The purpose of this utility model is the weak point that exists at above-mentioned prior art, provides a kind of and can satisfy normal use, and the ground maintenance personnel are reduced labor intensity, and is simple in structure, uses the catch of aircraft test run flexibly.
The technical scheme that its technical matters that solves the utility model adopts is: a kind of aircraft test run catch, comprise: the arc fagging of a support airplane wheel and the diagonal brace primary structure member that is fixed on arc fagging rear portion, it is characterized in that, described diagonal brace primary structure member is by riser that connects firmly arc fagging rear portion and the diagonal brace primary structure member that is fixed on the riser back side, and the stull primary structure member that laterally is fixed between riser and the diagonal brace primary structure member is formed, also be equipped with the handspike that is rotatably connected and has initiatively rocking arm in the triangular support framework both sides that constitute thus, also be connected with the crank block connecting rod mechanism of forming by the crank wheel fork on the rotational motion pair of described initiatively rocking arm and be assemblied in the road wheel that crank wheel is stuck.
Principle of work of the present utility model and beneficial effect are:
When handspike when the initiatively rocking arm rotating shaft is rotated, drive slide block and move.Slide block moves and forces the crank wheel fork to rotate around the crank connecting link axle.When handspike when the initiatively rocking arm rotating shaft rotates counterclockwise, slide block drives toggle-action lever simultaneously and clockwise rotates around the crank connecting link axle to be coupling near position motion of crank connecting link, and the road wheel that crank wheel is stuck is packed up.When handspike when the initiatively rocking arm rotating shaft clockwise rotates, slide block is towards moving away from the position of crank connecting link axle, toggle-action lever rotates counterclockwise under the control of slide block, the road wheel that crank wheel is stuck puts down.When slide block movement arrives the end points (the spacing dead point of mechanism) of chute, mechanism's dead center position will limit road wheel and pack up automatically.Thereby prevent the possibility that external force that road wheel in use produces is packed up wheel automatically.The test run catch of Zu Chenging thus, simple in structure, integral structure is reliable, and easy to use manufacturing expense is low flexibly, easily makes.
The utility model utilizes the motion of crank block connecting rod mechanism, according to the requirement before and after the aircraft utilization, utilizes the dead center position of piston crank mechanism self to reach self-locking the path of motion of handspike and running wheel.Realize the normal use of engine test catch.The crank block link rod frame structure of Cai Yonging wherein, guaranteed that not only aero-engine test run catch will directly pass in the ground run groove or directly passes on the ground, test run level ground both that contact with ground with test run catch when the carrying and take into account from aero-engine test run thrust, and, alleviated carrying labour intensity for the ground staff provides delivery means easy to use.Avoid the prior art body big and heavy greatly, used the defective of difficult.
Description of drawings
In order to further specify rather than limit above-mentioned implementation of the present invention, provide most preferred embodiment below in conjunction with accompanying drawing and example, thereby make details of the present invention and advantage become more obvious.
Fig. 1 is an organigram of the present utility model.
Fig. 2 is the local structure scheme drawing of the utility model crank block connecting rod mechanism.
Fig. 3 is the organigram of overlooking of Fig. 1.
Among the figure: 1. handspike, 2 swash plates, 3. top board, 4. diagonal brace primary structure member, 5. stull primary structure member, 6. road wheel, 7. wheel fork monaural, 8. crank wheel fork, 9. arc fagging, 10 curved baffle, 12. adapter shafts, 13. cover plate, 14. risers, 15. axle drive shafts, 16. auricles, 17. initiatively rocking arms.
The specific embodiment
Fig. 1, Fig. 2 have described the test run catch of being made by steel or aluminum.Wherein arc fagging 9 can be made up of three block plates.It is a contact aircraft main frame wheel, bears the primary structure member that transmits aero-engine thrust from the main frame wheel.The arc fagging 9 and the riser 14 that have gripping pattern pass through cover plate 13 weld togethers, constitute one and have certain thickness hollow riser supporter, to alleviate its weight.Connecting cover plate 13 main effects is to strengthen local stiffness, prevents the corrosion of rainwater to the test run catch, and baffle plate is played the effect of dimension shape.Laterally be fixed on the stull primary structure member 5 that constitutes spandrel frame between diagonal brace primary structure member 4 and arc fagging 9 rear portions, can adopt rectangular steel pipe or cylindrical steel to be welded to connect the triangularity framework.At least two diagonal ligament frameworks that are arranged parallel to each other that this spandrel frame is made up of diagonal brace primary structure member (4), stull primary structure member (5) connection board (14).Present embodiment is that the spandrel frame of three almost parallels is formed.Be to stop the displacement of catch, be fixedly connected with at the tail end of the diagonal ligament framework of described arrangement in parallel and only move resistance seat top board 3.Because diagonal brace primary structure member 4 and stull primary structure member 5 are main Force transmission partses of test run catch.So quarter bend one end at diagonal brace primary structure member 4 is welded with top board 3.Its end and riser 14 welding.When top board 3 has the ground groove on the test run level ground, be placed in the ground groove of proof ground, to withstand the edge of ground groove, the thrust that driving engine is transmitted passes to ground.When not having the ground groove, top board 3, stull primary structure member 5, arc fagging 9 and curved baffle 10 contact with ground together, and the thrust that driving engine is transmitted passes to ground.Stull primary structure member 5 links to each other with diagonal brace primary structure member 4 with riser 14, to riser 14 crossbeam that provides support.Arc fagging 9 provides erection support for crank wheel fork 7.In the present embodiment, the spandrel frame of being made up of diagonal brace primary structure member 4, stull primary structure member 5 and hollow riser supporter or arc fagging 9 is three frameworks that are arranged parallel to each other.The hypotenuse of two body side frames of spandrel frame is made of two diagonal brace primary structure members 4, all is fixed with auricle 16 on the both sides hypotenuse member of its framework, and is connected in the outside of both sides diagonal brace primary structure member 4 with bolt or rivet or pin.The end has the handspike 1 of the initiatively rocking arm 17 of V-arrangement arm plate, is ground maintenance personnel folding and unfolding road wheel, the handrail of carrying and implementation test run catch.Can adopt steel tube bending to form.The V-arrangement initiatively rocking arm 17 that connects handspike 1 can be added by a block plate machine and forms.Its end is connected with handspike 1 with bolt or rivet or pin, is the part of handrail.V-arrangement initiatively rocking arm 17 end fulcrums connect axle drive shaft 15 by the axis hole of described auricle 16, and initiatively rocking arm 17 can be rotated around axle drive shaft 15.In the rotating shaft of framework bilateral symmetry ground bonded assembly initiatively rocking arm 17 rotational motion pairs the crank block connecting rod mechanism of being made up of crank wheel fork 8 is housed, is connected in by pivot pin on the slide block 11 of crank wheel fork 8.Be shaped on the spacing length chute 18 of connecting crank slide block on the V-arrangement arm plate of described initiatively rocking arm.Slide block 11 is laid in the chute 18, and to constitute crank block connecting rod mechanism movement track limit dead point, the restriction road wheel is promoted by external force and packs up automatically.
Above-described only is the preferred embodiments of the present invention.Should be understood that; for the person of ordinary skill of the art; under the prerequisite that does not break away from the principle of the invention; can also make some distortion and improvement; such as; the utility model also can consider to be shaped in the described stull primary structure member outside chute of assembling connecting crank wheel fork slide block; described top board setting angle also can change according to different ground environments; connect not necessarily V-arrangement of handspike initiatively rocking arm; hollow riser supporter is hollow not necessarily; also can be solid construction, these changes and change should be considered as belonging to protection domain of the present utility model.
Claims (5)
1. aircraft test run catch, comprise: the arc fagging of a support airplane wheel and the diagonal brace primary structure member that is fixed on arc fagging rear portion, it is characterized in that, described diagonal brace primary structure member is by riser that connects firmly arc fagging rear portion and the diagonal brace primary structure member that is fixed on the riser back side, and the stull primary structure member that laterally is fixed between riser and the diagonal brace primary structure member is formed, also be equipped with the handspike that is rotatably connected and has initiatively rocking arm in the triangular support framework both sides that constitute thus, also be connected with the crank block connecting rod mechanism of forming by the crank wheel fork on the rotational motion pair of described initiatively rocking arm and be assemblied in the road wheel that crank wheel is stuck.
2. test run catch according to claim 1 is characterized in that, is shaped on the spacing length chute of connecting crank slide block on the V-arrangement arm plate of described initiatively rocking arm.
3. test run catch according to claim 1 is characterized in that, the arc fagging (10) and the riser (14) that have gripping pattern pass through cover plate (13) weld together, constitute one and have certain thickness hollow riser supporter.
4. test run catch according to claim 1 is characterized in that, at least two diagonal ligament frameworks that are arranged parallel to each other that described spandrel frame is made up of diagonal brace primary structure member (4), stull primary structure member (5) connection board (14).
5. test run catch according to claim 1 is characterized in that, the tail end of the diagonal ligament framework of described arrangement in parallel is fixedly connected with and only moves resistance seat top board (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU200520036382XU CN2934073Y (en) | 2005-12-05 | 2005-12-05 | Airplane test wheel fender |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU200520036382XU CN2934073Y (en) | 2005-12-05 | 2005-12-05 | Airplane test wheel fender |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN2934073Y true CN2934073Y (en) | 2007-08-15 |
Family
ID=38350761
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNU200520036382XU Expired - Lifetime CN2934073Y (en) | 2005-12-05 | 2005-12-05 | Airplane test wheel fender |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN2934073Y (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113218552A (en) * | 2021-03-23 | 2021-08-06 | 中国人民解放军空军工程大学 | Auxiliary equipment and method for evaluating installation thrust of aero-engine |
-
2005
- 2005-12-05 CN CNU200520036382XU patent/CN2934073Y/en not_active Expired - Lifetime
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113218552A (en) * | 2021-03-23 | 2021-08-06 | 中国人民解放军空军工程大学 | Auxiliary equipment and method for evaluating installation thrust of aero-engine |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| EE01 | Entry into force of recordation of patent licensing contract |
Assignee: Manufacturing center of Chengdu aircraft design and Research Institute Assignor: AVIC Chengdu Aircraft Design & Research Institute Contract record no.: 2011510000120 Denomination of utility model: Airplane test wheel fender Granted publication date: 20070815 License type: Exclusive License Record date: 20110810 |
|
| CX01 | Expiry of patent term |
Granted publication date: 20070815 |
|
| EXPY | Termination of patent right or utility model |